Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 82
Book Description
Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic and cubic twist variations along the span. All the twisted wings had 0deg twist at the 10-percent-semispan station and 6deg twist at the tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4deg to 20deg. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 x 10(exp 6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 x 10(exp 6) during tests at a stagnation pressure of 0.5 atmosphere.
Basic Pressure Measurements at a Mach Number of 1.43 on a Thin 45 Deg Sweptback Highly Tapered Wing with Systematic Spanwise Twist Variations
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 82
Book Description
Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic and cubic twist variations along the span. All the twisted wings had 0deg twist at the 10-percent-semispan station and 6deg twist at the tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4deg to 20deg. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 x 10(exp 6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 x 10(exp 6) during tests at a stagnation pressure of 0.5 atmosphere.
Publisher:
ISBN:
Category :
Languages : en
Pages : 82
Book Description
Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic and cubic twist variations along the span. All the twisted wings had 0deg twist at the 10-percent-semispan station and 6deg twist at the tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4deg to 20deg. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 x 10(exp 6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 x 10(exp 6) during tests at a stagnation pressure of 0.5 atmosphere.
Basic Pressure Measurements at a Mach Number of 1.43 on a Thin 45° Sweptback Highly Tapered Wing with Systematic Spanwise Twist Variations
Basic Pressure Measurements at a Mach Number of 1/43 on a Thing 45 Degree Sweptback Highly Tapered Wing with Systematic Spanwise Twist Variations
Author: John P. Jr Mugler
Publisher:
ISBN:
Category : Wall pressure (Aerodynamics)
Languages : en
Pages : 0
Book Description
Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic, and cubic twist variations along the span. All the twisted wings had 0 degrees twist at the 10-percent-semispan station and 6 degrees twist at he tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4 degrees to 20 degrees. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 X 10(6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 X 10(6) during tests at a stagnation pressure of 0.5 atmosphere.
Publisher:
ISBN:
Category : Wall pressure (Aerodynamics)
Languages : en
Pages : 0
Book Description
Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic, and cubic twist variations along the span. All the twisted wings had 0 degrees twist at the 10-percent-semispan station and 6 degrees twist at he tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4 degrees to 20 degrees. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 X 10(6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 X 10(6) during tests at a stagnation pressure of 0.5 atmosphere.
Effects of Three Spanwise Twist Variations on the Longitudinal Aerodynamic Characteristics of a Thin 45 Deg Sweptback Highly Tapered Wing at Transonic Speeds
Investigation at Mach Numbers from 0.80 to 1.43 of Pressure and Load Distributions Over a Thin 45 Degree Sweptback Highly Tapered Wing in Combination with Basic and Indented Bodies
Author: Thomas L. Fischetti
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 94
Book Description
Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number range from 0.80 to 1.125 and at a Mach number of 1.43 for a 45 degree sweptback cambered wing having a thickened root, an aspect ratio of 4.0, and a taper ratio of 0.15. Data were obtained for the wing in the presence of a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2.
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 94
Book Description
Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number range from 0.80 to 1.125 and at a Mach number of 1.43 for a 45 degree sweptback cambered wing having a thickened root, an aspect ratio of 4.0, and a taper ratio of 0.15. Data were obtained for the wing in the presence of a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2.
Aero/space Engineering
Pressure Distribution and Force and Moment Measurements of an 80 Deg Swept Wing with Twist and Camber at a Mach Number of 2.98
A Comparison at Mach Numbers Up to 0.92 of the Calculated and Experimental Downwash and Wake Characteristics at Various Horizonatl Tail Heights Behind a Wing with 45 Degrees of Sweepback
Author: Jack D. Stephenson
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 86
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 86
Book Description
Free-flight Measurements of the Zero-lift Drag of Several Wings at Mach Numbers from 1.4 to 3.8
Author: H. Herbert Jackson
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 32
Book Description
Measured and Theoretical Flow Fields Behind a Rectangular and a Triangular Wing Up to High Angles of Attack at a Mach Number of 2.46
Author: Frank J. Centolanzi
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 82
Book Description
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 82
Book Description